Rotorcraft with integrated light pipe support members

ABSTRACT

A radio controlled model rotorcraft implemented with features improving ease of flight and flight performance by increasing structural stability, increasing rotorcraft visibility and orientation awareness through the use of multifunctioning, configurable, and aesthetically pleasing components, while also increasing resistance to damage from crashes through use of impact and vibration absorbing components.

CROSS-REFERENCE TO RELATED APPLICATIONS

This application is a division of, and claims the benefit of the filingdate of, co-pending U.S. patent application Ser. No. 14/461,228 entitledROTORCRAFT WITH INTEGRATED LIGHT PIPE SUPPORT MEMBERS, filed Aug. 15,2014, which claims the benefit of the filing date of, U.S. provisionalpatent application Ser. No. 61/866,530 entitled QUADCOPTER WITHINTEGRATED LIGHT PIPE SUPPORT MEMBERS, filed Aug. 15, 2013, the entirecontents of which are incorporated herein by reference for all purposes.

BACKGROUND OF THE INVENTION

1. Field of the Invention

The present invention relates to radio controlled model rotorcrafts,and, more particularly, to means and methods of assembling and retainingcomponents of radio controlled model rotorcraft while enhancingaesthetically pleasing aspects of a rotorcraft.

2. Description of the Related Art

Radio controlled model rotorcrafts are propeller driven remotecontrolled vehicles configured for flight. Some important designconsiderations of particular importance in regard to radio controlledmodel rotorcrafts are flight performance and stability, ease of controlby the user, durability, aesthetics, and cost. Several characteristicsinherent to radio controlled model rotorcraft operation and appearanceadd to the difficulty in adequately addressing these designconsiderations. This is especially true as the number of propellersutilized by the radio controlled model rotorcraft is increased.

Radio controlled model rotorcraft are difficult to operate for severalreasons. For one, they are configured to move in three dimensions asopposed to two. Additionally, radio controlled model rotorcraft arecapable of reaching incredible speeds during flight, such as whendescending from high altitude, reducing the response time for a user tocorrect course to avoid a crash.

Users may also have difficulty discerning the orientation of the radiocontrolled model rotorcraft during flight, especially while performingaerial tricks or when operating a rotorcraft that has severalpropellers, causing the radio controlled model rotorcraft to have asimilar appearance from all sides. Confusion as to the orientation ofthe radio controlled model rotorcraft during flight greatly increasesthe likelihood of a loss of control by the user and a subsequent crash.

Stable flight requires the radio controlled model rotorcraft body besufficiently stiff to resist deflection and twisting during flight, inparticular, during acceleration. Increasing stiffness generally involvesusing more material and increasing the overall weight of the rotorcraft.Durability may be enhanced through the use of tougher materials and theaddition of protective components to sufficiently insulate sensitiveparts from vibration and impact, adding weight.

For flying vehicles weight increases are undesirable, however, sinceweight increases degrade performance. Further, weight increase mayresult in increased cost if higher power or additional thrust-generatingcomponents are used to compensate for the additional weight.

A need exists for a radio controlled model rotorcraft implemented withdesign features that simultaneously promote flight performance andstability, ease of control by the user, and durability without incurringcost or weight penalties, and while also incorporating desirableaesthetic attributes.

SUMMARY

Provided is an radio controlled model rotorcraft implemented withfeatures improving ease of flight and flight performance by increasingstructural stability, increasing rotorcraft visibility and orientationawareness through the use of multifunctioning, configurable, andaesthetically pleasing components, while also increasing resistance todamage from crashes through use of impact and vibration absorbingcomponents.

BRIEF DESCRIPTION OF THE DRAWINGS

For a more complete understanding of the present invention and theadvantages thereof, reference is now made to the following DetailedDescription taken in conjunction with the accompanying drawings, inwhich:

FIG. 1 is a perspective view of a quadcopter rotorcraft;

FIG. 2 is a top view of a quadcopter rotorcraft with a pod cover removedfor clarity;

FIG. 3 is a bottom view of a quadcopter rotorcraft;

FIG. 4 is an exploded view of a quadcopter rotorcraft;

FIG. 5A is a first cross-sectional view of a rotor assembly of aquadcopter rotorcraft taken along line 5A-5A shown in FIG. 2;

FIG. 5B is a cross-sectional view of a second fastener assembly takenalong line 5B-5B shown in FIG. 5A;

FIG. 5C is a cross-sectional view of a third fastener assembly takenalong line 5C-5C shown in FIG. 5B;

FIGS. 6A and 6B are a perspective and a bottom view, respectively, of asupport member;

FIG. 7 is a bottom view of a first arm showing wire channels;

FIG. 8 is a perspective view of a foot;

FIG. 9 is second cross-sectional view of a rotor assembly of aquadcopter rotorcraft taken along line 5A-5A shown in FIG. 2;

FIG. 10 is a third cross-sectional view of a rotor assembly of aquadcopter rotorcraft taken along line 5A-5A shown in FIG. 2, whereinthe line 5A-5A is taken through a torque transfer assembly;

FIGS. 11A, B, and C are perspective, top, and rear views, respectively,of a base of a quadcopter rotorcraft;

FIG. 12 is a bottom view of a center pod assembly with a base removedfor clarity;

FIG. 13A is a bottom view of a quadcopter rotorcraft; FIG. 13B is across-sectional view taken along line 13B-13B, the view showing alocator recess; and

FIG. 13C is a cross-sectional view taken along line 13C-13C, the viewshowing a printed circuit board assembly (PCBA) mounted within a housingformed by a cover and base of a quadcopter rotorcraft.

DETAILED DESCRIPTION

In the following discussion, numerous specific details are set forth toprovide a thorough understanding of the present invention. However,those skilled in the art will appreciate that the present invention maybe practiced without such specific details. In other instances,well-known elements have been illustrated in schematic or block diagramform in order not to obscure the present invention in unnecessarydetail. Additionally, and for the most part, details concerningwell-known features and elements have been omitted inasmuch as suchdetails are not considered necessary to obtain a complete understandingof the present invention, and are considered to be within theunderstanding of persons of ordinary skill in the relevant art.Additional details are shown in the Appendix attached hereto andincorporated by reference for all purposes.

Referring first to FIG. 1, a particular embodiment of a radio controlledmodel rotorcraft, a rotorcraft 1000, is shown. According to theembodiment shown, the rotorcraft 1000 may comprise four rotorassemblies: a first rotor assembly 100; a second rotor assembly 200; athird rotor assembly 300; and, a fourth rotor assembly 400. Therotorcraft 1000 may further comprise a center pod assembly 500.

Each of the first rotor assembly 100, the second rotor assembly 200, thethird rotor assembly 300, and the fourth rotor assembly 400 may beimplemented with a first propeller 104, a second propeller 204, a thirdpropeller 304, and a fourth propeller 404, respectively. A rotorcraftprovided with four propellers, such as the rotorcraft 1000 shown anddescribed herein, may be referred to as a quadcopter. Airborne motion ofthe rotorcraft 1000 may be controlled by rotation of the propellers 104,204, 304, and 404 and by adjustment of the angular velocities of eachpropeller by known methods to provide adjustment of thrust and torque tosupport stable flight of the rotorcraft 1000.

Each of the rotor assemblies 100, 200, 300, and 400 may couple to thecenter pod assembly 500 at the inboard end of the rotor assembly 100,200, 300, and 400 and may extend, along its length, away from the centerpod assembly 500. The rotor assemblies 100, 200, 300, and 400 mayrigidly couple the propellers 104, 204, 304, and 404 to the center podassembly 500, fixing the position and orientation of each respectivepropeller 104, 204, 304, and 404 relative to each other and to thecenter of mass, C1, of the rotorcraft 1000.

Referring to the embodiment shown in FIGS. 1 and 2, the propellers 104,204, 304, and 404 may be arranged in a substantially rectangularconfiguration about the center of mass C1, which may be within thecenter pod assembly 500. In a particular embodiment, for example, thedistance between the axis of rotation of opposing propellers may beabout 23.5 centimeters (cm.) (i.e. between propellers 104 and 304),while the distance between the axis of rotation of adjacent propellersmay be about 16.6 cm. (i.e. between propellers 104 and 204). In anembodiment, the propellers 104, 204, 304, and 404 may be positioned at asubstantially equal distances from the center of mass C1.

In alternative embodiments, a radio controlled model rotorcraft may beprovided with more, fewer, or additional components than those shown inthe particular embodiment, the rotorcraft 1000, described herein.Additionally, in alternative embodiments, a radio controlled modelrotorcraft may have a different component arrangement than that shown inthe particular embodiment, the rotorcraft 1000, described herein.Specifically, alternative embodiments may include more or fewer rotorassemblies that may be positioned in a substantially triangular orcircular configuration about the rotorcraft center of mass.Additionally, in an embodiment, the rotorcraft center of mass may belocated at a point external to the center pod assembly 500.

The components of the first rotor assembly 100 of a particular radiocontrolled model rotorcraft embodiment, the rotorcraft 1000, aredescribed herein. The components of the rotor assemblies 200, 300, and400 may have substantially similar construction and features as thecorresponding components of the first rotor assembly 100. Further, thecomponents of the rotor assemblies 200, 300, and 400 may performsubstantially the same functions as the corresponding components of thefirst rotor assembly 100. The convention of describing components ofonly the first rotor assembly 100 is adopted for the purpose of avoidingunnecessary and repetitive language, only, and shall not foreclose fromthe scope of this disclosure a wide range of variations, modifications,changes and substitutions that would be understood by those skilled inthe art as expressly, or implicitly, disclosed here.

Referring to FIGS. 2-10, the first rotor assembly 100 may include afirst arm 102, a first propeller 104, a first support member 106, andfastener assemblies 108A-D In alternative embodiments, additional,fewer, or different components than those shown may be provided.

In an embodiment, the first arm 102 may operatively couple the firstrotor assembly 100 to the center pod assembly 500, as shown in FIG. 2.Referring to FIGS. 5A and 7, the first arm 102 may include an inboardend 103, an outboard end 105, wire channels 110, a cut through portion114, and a plurality of coupling members. In a particular embodiment,the first arm 102 may be provided with additional, fewer, or differentcomponents.

The first arm 102 may be comprised of a single piece of rigid orsemi-rigid material. For example, in a particular embodiment, the firstarm 102 may be made from nylon or other similar material. It will beunderstood by persons of ordinary skill in the art that the first arm102 may alternatively be made from any other suitable material (e.g.plastics, metals, wood, and composites) based on the requirements forflight of the particular radio controlled model rotorcraft embodimentand other structural, aesthetic, and cost factors.

As shown in FIGS. 4 and 5, in an embodiment, the first arm 102 maycouple to, or, alternatively, be integrally formed with the center podassembly 500 at the inboard end 103. The first arm 102 may extend alongits length in a direction away from the center pod assembly 500. Asviewed from the side, the first arm 102 may have a downwardly slopingarced profile, whereby the outboard end 105 is disposed below theinboard end 103. Alternatively, the first arm 102 may have a profilethat is substantially linear, dog-legged, or the like, or may have aprofile with multiple bends or curves.

As shown in FIGS. 1, 4, 5B, and 5C, the first arm 102 may have a curved,substantially “C” shaped, outer cross sectional shape, oriented with theapex of the curve facing upward. In an embodiment, and as shown in FIGS.5A and 5B, within the inner portion of the curved cross section thefirst arm 102 may be provided with an interlocking slot 120.

The interlocking slot 120 may have an open end facing substantiallydownward. The interlocking slot 120 may abut the inner portion of thecurve defining the outer cross sectional shape of the arm 102substantially at the apex of the curve. The interlocking slot 120 may beformed from two substantially parallel flanges extending inward from theinner surface of the first arm 102 curved outer cross section. Theinterlocking slot 120 may extend a distance along the length of thefirst arm 102 from the outboard end 105 and terminating at the cutthrough portion 114. The interlocking slot may function as a fasteningfeature, as described below, in reference to fastener assembly 108B.

Viewing the first arm 102 from above, as shown in FIG. 2, the first arm102 may be curved along each side, whereby the first arm 102 may bethinner at the outboard end 105 and wider at the inboard end 103. In analternative embodiment, the first arm may have a substantially uniformwidth along its length, or, may widen along its length such that theoutboard end 105 is wider than the inboard end 103.

Referring to FIG. 7, the first arm 102 may be provided with wirechannels 110A and 110B for retaining and routing electrical wires A, Balong the length of the first arm 102. In an embodiment, wires A, B maybe routed between rotor assembly 100 components near the outboard end105 of the first arm 102, like the first motor 101, for example, andcontrols components that may be enclosed within the center pod assembly500, like the PCBA 506, for example, to support powered flight of therotorcraft 1000.

Each wire channel 110A and 110B may extend along the length of the firstarm 102 from the inboard end 103 to the outboard end 105 along theunderside of the first arm 102. The wire channels 110A and 110B may bepositioned along either side of interlocking slot 120. In an embodiment,the first arm 102 may have fewer or more wire channels 110 that mayextend along only a portion of the length of the first arm 102, or,alternatively, along substantially the entire length of the first arm102.

Each wire channel 110A, B may have dimensions, such as width w, and maybe provided with retaining tabs 111A-C and 113 A-C, respectively, forholding wires A, B in place and substantially resisting migration ofwires within each wire channel 110A, B. In a particular embodiment, forexample, the width, w, of each wire channel 110A, B may be about 0.65cm. The retaining tabs 111, 113 may extend laterally across a portion ofthe width, w, of the respective wire channels 110 so that the wires A, Bmay be pushed around the retaining tabs 111, 113 and into place in thewire channels 110A, B. Alternatively, the retaining tabs 111, 113 mayextend across substantially the entire width, w, of the wire channels110A, B with wires A, B being fed through the gap formed.

In an alternative embodiment, the wire channels 110 A, B may be providedwith fewer or more retaining tabs 111, 113 than shown in FIG. 7.Further, in an alternative embodiment, the wire channels 110A, B may beprovided with zero retaining tabs 111, 113. In such embodiments, thewire channels A, B may be implemented with other retaining devices, suchas external clips, ties, and the like. Alternatively, the wire channels110A, B may not include any retaining devices or external fasteners.

Referring to FIG. 7, the first arm 102 may include a cut through portion114 forming an opening for seeing through a portion of the first arm102. In an embodiment, the cut through portion 114 may be disposed alongtop surface of the first arm 102, substantially centered about the apexof the outer curved surface of the first arm 102 and extending adistance along the length of the first arm 102. In the embodiment shown,the cut through portion 114 may have a substantially trapezoidal shapedperimeter.

In alternative embodiments, the first arm 102 may be provided with zero,one, or a plurality of cut through portions 114. Further, in analternative embodiment, the cut through portion, or portions, 114 may bepositioned at other locations along the outer surface of the first arm102 and, additionally, may have s different perimeter shape, or shapes.For example, in an embodiment, the first arm may be provided with aplurality of circular cut through portions 114 disposed in an irregularpattern along the length of the outer surface of the first arm 102.

The first arm 102 may also include a plurality of coupling memberscomprising components of the fastening assemblies 108A-D for couplingwith, receiving, or partially forming other rotorcraft 1000 components,such as the motor 101, the first support 106, the motor receptacleassembly 160, the propeller shaft receptacle assembly 170, and thetorque transfer assembly 180. The coupling members of the first arm 102are described in detail below, and in reference to fastening assemblies108A-D.

Turning now to the top-view of the rotorcraft embodiment, the rotorcraft1000, shown in FIG. 2, the first propeller 104 is shown. In a particularembodiment, the first propeller 104 may have two blades and a diameterof 140 millimeters (mm). In alternative embodiments, the propeller 104may be implemented with a different quantity of blades having a largeror smaller diameter. The first propeller 104 may be rotatably coupled tothe outboard end 105 of the first arm 102, as will be described furthersubsequently, and in reference to the propeller shaft receptacleassembly 170 and the torque transfer assembly 180.

In an embodiment, the propellers 104, 204, 304, and 404 may comprisematched pairs of counterclockwise and clockwise rotating propellers toprovide a stable spinning configuration in accordance with known methodscomprising the prior art. It will be understood by persons of ordinaryskill in the art that the number of blades, diameter, pitch, andspinning configuration may be varied to support agility, stability, andefficiency of a rotorcraft, such as the rotorcraft 1000 describedherein, in flight.

Turning now to FIGS. 4-10, several views of the first support member 106are shown. According to the embodiment shown, the first support member106 may perform many functions, including: providing configurable anddecorative lighting along the length of the first rotor assembly 100 foraiding users in identifying directional orientation of the rotorcraft1000 during flight; providing structural support to the first arm 102,thereby increasing the stiffness of the rotor assembly 100 for morestable flight; receiving, coupling, or securing other components to therotorcraft 1000.

Importantly, in the context of flying devices such as radio controlledmodel rotorcrafts, having a single component perform multiple functions,as the first support member 106 may, may allow for incorporation ofadditional features into the device without incurring a corresponding“mass penalty,” resulting in a potentially less costly and more capabledevice. Additionally, the number of component parts may be reduced, andmay provide the benefits of easier assembly and maintenance through areduction in the number of external fasteners needed, for example,screws, clips, inserts, and the like.

As shown in FIG. 3, the first support member 106 may couple to thecenter pod 500 and to the first arm 102. As shown in FIGS. 4-6B, in anembodiment, the first support member 106 may include an exposed surface116, an inboard end 122, an outboard end 124, an indented portion 126,and a plurality of coupling members comprising components of thefastening assemblies 108A-D. In alternative embodiments, the firstsupport member may include fewer, additional, or different components.

In an embodiment, the first support member 106 may comprise a piece ofsemi-rigid or rigid material that may be transparent or semi-transparentand capable of distributing light received from a light sourcesubstantially throughout its volume, illuminating the surfaces of thetransparent or semi-transparent material. For example, the first supportmember 106 may be made from an acrylic, polycarbonate, or other likematerial.

The material may appear substantially clear or, alternatively, may havea color. Coloring may be provided through any known methods, such asthrough tinting, coating, or other known method comprising the priorart. Further, whether the material appears substantially clear, or has acolor, the material may be capable of receiving light of a specificcolor and emitting light of a different color when illuminated. Forexample, the first support member 106 may be composed of a substantiallyclear material having the properties described above and may, whenreceiving white light illuminate and emit light of another color,perhaps green. In another example, the first support member may have acolor, perhaps red, and may illuminate and emit red light upon receivingwhite light or colored light.

In certain embodiments, the first support member 106 may be madeentirely of material having the rigidity and illuminatingcharacteristics described above, so that substantially the entire outersurface of the first support member 106 may be illuminated when light isreceived by any portion of the support member 106. Further, in such anembodiment, the first support member 106 may be made from a single pieceof material having the properties described above.

In alternative embodiments, the first support member 106 may be composedof two or more materials, with at least one of the materials having therigidity and illuminating properties described above. In such anembodiment, the portion of the first support member 106 composed of thematerial capable of being illuminated may be implemented so that itextends from the inboard end 122 along the length of the first supportmember 106, and toward the outboard end 124. Further, in such anembodiment, the portion of the first support member 106 composed of thematerial capable of being illuminated may extend along substantially theentire length of the first support member 106.

As shown FIGS. 3, 6A, and 6B, the first support member 106 may couple tothe center pod assembly 500 at the inboard end 122 and extend along itslength in a direction away from the center pod assembly 500. Viewed fromthe side, as shown in FIG. 9, the first support member 106 may have adownwardly sloping arced profile similar to that of the first arm 102,whereby the outboard end 124 is disposed below the inboard end 122. Inalternative embodiments, the first support member 106 may have a profilethat is substantially linear, dog-legged, or the like, or may have aprofile with multiple bends or curves.

Referring to FIG. 5A, the first support member 106 may be provided withan exposed surface 116. The exposed surface may extend through thecut-through portion 114 of the first arm 102, when the first arm 102 andfirst support member 106 are coupled. The exposed surface 116 maycomposed of an illuminating material as described above so that aportion of the illuminated first support member 106 may be viewed fromabove the rotorcraft through opening formed by the cut through portion114 of the first arm 102.

As shown in FIGS. 4 and 5A, the exposed surface 116 may be disposedalong the side of the first support member 106 to which the first arm102 couples, protruding upward from the body of the support arm 106. Theexposed surface 116 may extend a distance along the length of the firstsupport member 106. The position of exposed 116 may align with theposition of the cut through portion 114 of the first arm 102 when thefirst arm 102 and first support member are coupled.

The exposed surface 116 may be configured to have a perimeter shapesubstantially coincident with the perimeter shape of the cut throughportion 114 of the first arm 102. In the embodiment shown, the cutthrough portion 114 may have a substantially trapezoidal shapedperimeter. The exposed surface 116 may fit within the opening in thefirst arm 102 formed by the cut through portion 114. Further, theexposed surface 116 may protrude to a height above the surface of thefirst support member 106 sufficient to substantially “fill” the openingformed in the first arm 102 by the cut through portion 114.

In alternative embodiments, the quantity, location, perimeter shape, andheight of the exposed surface, or surfaces 116, may vary in accordancewith the corresponding features of the cut through portion, or portions114, of the first arm 102, so that the exposed surface 116 may “fill”the opening formed in the first arm 102 by the cut through portion 114.

Referring to FIGS. 5A-C, the first support member 106 may have a curved,substantially “C” shaped, outer cross section extending along theportion of its length outboard of the exposed surface 116. The curvedcross sectional shape may be oriented with the apex of the curvedsurface facing substantially downward and with the “open end” facingupward and toward the first arm 102. The first support member 106 mayhave an outer cross section configured to mate to the first arm 102along the length of each component. The outer cross section size of thefirst support member 106 may be sized to fit within, and extend into,the downwardly facing open end of the first arm 102 formed by the innersurface of the outer cross section of the first arm 102.

The first support member 106 may be provided with a ridge 118 extendingalong a portion of the length of the first support member 106. The ridge118 may be disposed along the inner surface formed by the substantially“C” shaped cross section of the first support member 106 and protrude a.The ridge 118 is described further below, in regard to the fasteningassembly 108B.

As shown in FIG. 6A, the first support member 106 may be provided withan indented portion 126 disposed at the inboard end 122 and extendinginto the body of the first support member 106 along the length of thefirst support member 106. The indented portion 126 may form an open areawithin the body of the first support member 106 providing clearance fora light source 511 to be partially inserted into when the first supportmember 106 is coupled to the center pod assembly 500, as describedbelow. The indented portion 126 may extend into the first support member106 along the length of the first support member 126 and terminate justinboard of the exposed surface 116.

Viewed from below, as shown in FIG. 3, the first support member 106 mayhave a profile that is curved along each side so that the width of thefirst support member 106 thins along the length of the first supportmember 106, with the first support member 106 wider at the inboard end122 and thinner at the outboard end 124. In an alternative embodiment,the first arm may have a substantially uniform width along its length,or, may widen along its length such that the outboard end 124 is widerthan the inboard end 122.

The profile shape of the support member 106 may be substantially similarto the profile shape of the first support member shown in FIG. 2 anddescribed above. The first support member 106 profile width may besufficiently less than that of the first arm 102 along the length ofeach component, allowing for the first support member to be slid intoand mate with the first arm 102.

Referring to the embodiment shown in FIGS. 3 and 5A, the first supportmember 106 may be removably coupled to the first arm 102. The firstsupport member 106 may structurally support the first arm 102 againstdisplacement from flexing or twisting that may result from accelerationor impact during operation of the rotorcraft 1000. The coupled first arm102 and first support member 106 may exhibit increase stiffness alongthe length of the rotary assembly 100 and provide for more stable flightof the rotorcraft 1000. Additionally, the coupled first arm 102 andfirst support member 106 partially enclose rotary assembly components,such as the motor 101, for example, and may trap and protect rotorcraft1000 components, such as the wires A, B routed within wire channels110A, B as shown in FIGS. 5A, B (not labeled).

The rotary assembly 100 may include the fastener assemblies 108 A-C forcoupling the first support member 106 to the first arm 102. Inalternative embodiments, the first support member 106 may be coupled tothe first arm 102 using some, all, or none of the fastener assemblies108 A-C.

Referring to FIGS. 4 and 5, a first fastener assembly 108A may comprisea hook member 138 extending from the outboard end 124 of the firstsupport member 106. The hook member 138 may be configured to fit withinand extend at least partially through an aperture 140 formed in theoutboard end 105 of the first arm 102. An extension of the hook member138 may catch and extend over a bar portion 142 (also shown in FIG. 5A)of the aperture 140 when the hook member 138 is inserted in the aperture140 to secure the outboard end 124 of the first support member 106 tothe outboard end 105 of the first arm 102.

Referring to FIGS. 4, 5A, and 9, the first fastener assembly 108A mayfurther comprise a cup member 144 formed from curved side portions 146,148 and a bottom surface 150. Edges of the side portions 146, 148 andthe bottom surface 150 may align with edges of the aperture 140 formedin the outboard end 105 of the first arm 102 to form a housing that maybe a motor cradle assembly 160 for receiving and partially enclosing amotor 101 as is described further, below. When the hook member 138 isinserted into the aperture 140, the first support member 106 may besecured against displacement of the first support member 106 in theinboard-outboard direction.

Referring to FIGS. 5A and 5B, a second fastener assembly 108B maycomprise interlocking tabs 112A-C extending from the ridge 118 adistance further inward and toward the center of “C” shaped crosssection of the first support member 106. The ridge 118 may extend alonga length of the first support member 106 as described above. Each tab112A-C is configured to mate with the interlocking slot 120 positionedon an underside of the first arm 102. Each tab 112A-C may fit into aportion along the length of the interlocking slot 120 to establish asnug fit.

When the interlocking tabs 112A-C are fit into the interlocking slot120, the first support member 106 may be secured against displacement ofthe first support member 106 in the inboard-outboard direction and mayresist twisting of the joined structure comprising first support member106 and first arm 102. Although the embodiment shown is implemented withthree interlocking tabs 112, in an alternative embodiment fewer, oradditional, interlocking tabs 112 may be provided. For example, in anembodiment, one continuous interlocking tab 112 may be provided that mayextend along substantially the entire length of the correspondinginterlocking slot 120.

Referring to FIGS. 5A, 5C, 6A, 6B, and 7, a third fastener assembly 108Cmay comprise a series of first snap tabs 128A-C and second snap tabs130A-C of the first support member 106. The first snap tabs 128A-C andsecond snap tabs 130A-C may be disposed opposite one another along theouter surface of the “C” shaped outer profile of the first supportmember 106 near the open end of the “C”. The first snap tabs 128A-C andsecond snap tabs 130A-C may protrude a distance outward from the outersurface of the first support member 106 and extend along a portion ofthe length of the first support member 106. The first snap tabs 128A-Cand second snap tabs 130A-C, respectively, may fit under and engage afirst lip 132 and a second lip 134, respectively, of the first arm 102when the first support member 106 is slid into the underside of thefirst arm 102 as described above.

Although the embodiment shown is implemented with three first snap tabs128 and second snap tabs 130, in an alternative embodiment fewer, oradditional, snap tabs 128 and second snap tabs 130 may be provided. Forexample, in an embodiment, continuous snap tabs 128, 130 may be providedand may extend along substantially the entire length of thecorresponding lips 132, 134.

The first lip 132 and the second lip 134, respectively, of the first arm102 may be disposed opposite one another along the inner surface of the“C” shaped outer profile of the first arm 102 substantially at the openend of the “C”. The first lip 132 and the second lip 134 may protrude adistance inward from the inner surface of the first arm 102 and extendalong a portion of the length of the first arm 102.

The first lip 132 and second lip 134 may each be a single, continuouslip extending along substantially the whole length, or, alternatively,only a portion of the length of the first arm 102. In anotheralternative embodiment, additional first lips 132 and second lips 134may be provided, with each lip 132, 134 extending along a portion of thelength of the first arm 102 corresponding to a location of a snap tab128, 130 of the first support member 106.

The first snap tabs 128A-C and the second snap tabs 130A-C may lock thefirst support member 106 to the first arm 102, when the snap tabs 128,130 are engaged with the first lip 132 and the second lip 134,respectively. Under a heavy impact, flexibility in the support member106 may allow the first snap tabs 128A-C and the second snap tabs 130A-Cto unsnap from the respective first lip 132 and the second lip 134 toprevent structural damage to other portions of the rotorcraft 1000.

The rotary assembly 100 may also include a fastener assembly 108 D, asshown in FIGS. 6A, 6B, and 10, for removably coupling the first supportmember 106 to the center pod assembly 500 at the inboard end 122 of thefirst support member 106.

Referring to FIGS. 6A, 6B, and 10, the fourth fastener assembly 108D maycomprise a collar 135 and a hoop member 121. The hoop member 121 may bedisposed at the inboard end 122 of the first support member 106 extend adistance along the length of the first support member 106 toward theoutboard end 124. The hoop member 121 may further extend about the crosssection of the inboard end 122 of the first support member 106, having aboundary shape as best shown in FIG. 6A.

The hoop member 121 may abut the collar 135, with the collar 135disposed outboard to the hoop member 121 and extending about the crosssection of the inboard end 122 of the first support member 106. Thecollar 135 may form a groove around a portion of the cross section ofthe first support member 106. The collar 135 may have a boundary shapedsimilarly to that of the hoop member 121 but sized slightly smaller thanthat of the hoop member 121 along each length defining the boundaryshape of the hoop member 121.

The hoop member 121 and the collar 135 may be configured to couple withthe center pod assembly 500, by engaging the collar 135 with an openingformed in the center pod assembly 500 with a perimeter shape and sizesubstantially coincident to the boundary shape and size of the collar.The hoop member may then be trapped within the opening formed and securethe first support member to the center pod assembly 500 as describedbelow with respect to FIG. 10. When the hoop member 121 and collar 135are coupled to the center pod assembly 500, the first support member 106may be secured against disengagement of the first support member 106from the center pod assembly 500, and may resist twisting of the firstsupport member 106.

When the first support member 106 is mated with the first arm 102, thestructure of the combination of first arm 102 and first support member106 is configured to substantially prevent flexing and twisting of thefirst arm 102 and displacement of the motor relative to the center podassembly 500. Minimizing flexing and twisting of the first arm 102promotes stability of control over the rotorcraft 1000 during flight andmay prevent crashes.

Additionally, with the first support member 106 coupled to the first arm102 and the center pod assembly 500 using fastening assemblies 108A-D,as described, the need for external fasteners, such as screws, clips,inserts, and the like, to couple the rotary assembly 100 components maybe greatly reduced, or eliminated. Coupling the rotary assembly 100components as described above may provide the additional advantages ofease of assembly and disassembly, while allowing for removable couplingof the rotary assembly 100 components, notably, the first support member106.

In the embodiment shown and described above, the support members 106,206, 306, and 406 may be both removably coupled to the rotorcraft 1000and be configured to function as a light pipe, capable of illuminatingalong the outer surfaces of the support members 106, 206, 306, and 406when receiving light from light source.

The rotorcraft 1000 may further be implemented with a support membercolor arrangement configurable by the user through removal andreplacement of an undesired support member with one having the desiredcolor characteristics at each rotor assembly. For example, a user mayconfigure both forward facing support members of rotorcraft 1000 toilluminate red by replacing the forward facing support members withsupport members configured to illuminate red in response the lightreceived from the light source within the center pod assembly. Users mayconfigure the light arrangement in accordance with their colorpreference. The configurable light pipe feature may allow for therotorcraft 1000 to be easier to fly in low visibility settings, such asin the evening, or in an indoor environment, and may also aid the userby allowing the orientation of the rotorcraft to be easily discerned,based on the support member color configuration, during flight. Theability to determine orientation of the rotorcraft 1000 may be furtherenhanced by the cut through portion 114 of the first arm, through whichthe illuminated light from the support member below may be seen.

With the color configuration viewable from both the top and bottom ofthe rotorcraft 1000, the orientation may be determined by the user whileperforming tricks during flight that may cause the rotorcraft to be inan inverted position, as well as in settings where the user may operatethe rotorcraft 1000 from an elevated position.

The first support member 106 may further be configured to provideaesthetically pleasing lines and features. For example, when the firstsupport member 106 is mated with the first arm 102, the first supportmember 106 may be shaped to have a curvature that follows or complementsthe curvature of the first arm 102 and the curvature of the center podassembly 500, as shown in FIGS. 1 and 5A.

The first arm 102 and first support member 106, as coupled may also formone or more housings for receiving and partially enclosing other rotaryassembly 100 components. Referring to FIGS. 3, 9, and 10, the first arm102 and first support member 106 may couple at the outboard ends 105,124 of each to form a housing that may be a first motor cradle 160 forreceiving and at least partially enclosing a motor 101.

In the embodiment shown, the first motor cradle 160 may comprise a motorchannel 162 extending through a portion of the outboard end 105 of thefirst arm 102 and in a direction that may be substantially perpendicularto the plane P1 in which the first propeller 104 rotates. It will beunderstood by those of ordinary skill in the art that alternativeembodiments may include a motor channel 162 oriented in a direction notsubstantially perpendicular to the plane of rotation of the propellers,with the motor provided with a torque transfer assembly configured toaccommodate the specific motor channel 162 orientation. When the firstsupport member 106 is fully coupled to the first arm 102, the cup member144 may form a bottom portion of the motor cradle 160 and maysubstantially close the motor channel 162 at a bottom end 161.

In the embodiment shown, the motor channel 162 may partially form asubstantially cylindrical housing with dimensions configured to fit acylindrically shaped motor, e.g. the first motor 101. In alternativeembodiments, the motor channel 162 may be configured to partially form ahousing of a different shape, configured to accommodate the particularshape of the motor provided. A bottom portion of the first motor 101 maybe configured to rest in the cup member 144. The diameter of the motorchannel 162 may be configured to substantially prevent shifting of thefirst motor 101 within the motor channel 162.

In a particular embodiment, the first motor 101 may comprise a corelessmotor of about 8.5 mm by 20 mm (8.5×20) in size and configured toprovide about 3.5 to 6.0 watts (W). The first motor 101 may have anoperating voltage of about 2.0-4.0 volts (V), with a no-load speedbetween 40000 and 50000 revolutions per minute (rpm). The motor 101 maybe configured to rotate the motor shaft 109 in either of two directionsabout the lengthwise axis of the motor shaft 109, as desired. It will beunderstood by persons of ordinary skill in the art that other types andsizes of motor may be utilized to support operation of the embodimentsof the rotorcraft 1000.

Referring to FIG. 4, the motor channel 162 may further comprise acut-out 165 extending through a side portion of the motor channel 162.The cut-out 165 may conserve materials and reduce weight of the outboardend 105 of the first arm 102. The cut-out 165 may comprise a sizeconfigured to provide sufficient structure to block displacement of thefirst motor 101 through the cut-out 165.

Referring to FIGS. 5A, 9, and 10, a motor channel rim forming an openingfor a motor shaft may extend around a top end 163 of the motor channel162 opposite from the cup member 144. A top portion of the first motor101 comprising a motor shaft 109 and motor gear 115, such as a pinion orbevel gear, may extend through the motor shaft opening above the motorchannel rim 164. The motor channel rim 164 may comprise a diameterconfigured to constrain the first motor 101 within the motor channel rim164 and prevent the motor 101 from shifting within the motor channel162.

Referring to FIG. 6B, the bottom surface 150 of the first support member106, which may form the cup member 144, may comprise a foot hole 141.The foot hole 141 may comprise a size and shape configured to snugly fita foot 143. The foot 143 may function as a landing support and as ashock absorber protecting the first motor 101 from impact forces.

Referring to FIG. 8, in an embodiment, the foot 143 may comprise a firstflange 145 and a second flange 147 coupled by a stem 149. The foot 143may comprise an elastic and resiliently deformable material, such asrubber, foam, and the like.

The second flange 147 may comprise a shape such as a substantially disk,conical or semi-conical shape. The shape of the second flange 147 may beconfigured to be compressed, twisted, or deformed to fit into the foothole 141 (shown also in FIG. 6B) for installation of the foot 143. Oncefit and pushed through the foot hole 141, the second flange 147 mayexpand and return to its original shape. In a particular embodiment, thesecond flange 147 may have a diameter of about 0.65 cm. and configuredto resist removal of the foot from the foot hole 141, while the foothole may have a diameter of about 0.42 cm.

The first flange 145 may comprise a shape to support use of the firstflange 145 as a landing support and as a shock absorber protecting thefirst motor 101. A foot having substantially the same construction maybe positioned at a foot hole of each other support member 206, 306, 406to operate in combination to cushion landings and crashes of therotorcraft 1000.

The shape of the first flange may comprise a semi-spherical shape havinga height and base diameter. In some embodiments, the height may compriseabout 0.3 cm. and the base diameter may comprise about 0.8 cm. A centralaxis of the foot 143 and central axis of the motor 101 may align alongline C, shown in FIG. 10, to provide protection from shocks to the motor101 at the bottom end of the motor 101.

Referring to FIGS. 3, 5A, and 9, in an embodiment, a portion of thefirst arm 102 may extend in an outboard direction from the motor channel162 to form a housing that may be a propeller shaft cradle 170. Thepropeller shaft cradle 170 may be configured to support rotation of apropeller shaft 107 coupled to the first propeller 104. The propellershaft cradle 170 may comprise a propeller shaft channel 174 extendingthrough a portion of the outboard end 105 of the first arm 102 in adirection substantially perpendicular to the plane P1 in which the firstpropeller 104 rotates. The propeller shaft channel 174 may be offsetfrom the motor channel 162 in an outboard direction relative to theinboard end 103 of the first arm 102.

The propeller shaft channel 174 may comprise a diameter configured toreceive a propeller shaft 107 and bearings 117A, B for supportingrotation of the shaft 107. The propeller shaft channel 174 may be openat a top end to allow the propeller shaft 107 to extend above the topend of the propeller shaft channel 174 and to couple to the firstpropeller 104.

The propeller shaft cradle 170 may further comprise spokes 175A-Eextending from the outer surfaces of the propeller shaft channel 174.The spokes 175A-E may extend to a gear rim 176. The gear rim 176 maycomprise a substantially circular shape centered about the propellershaft channel 174, and the circular shape may extend in a planesubstantially parallel to the plane in which the first propeller 104rotates. The spokes 175A-E may provide structural support and stabilityto the gear rim 176 and substantially prevent flexing of the gear rim176 relative to the propeller shaft channel 174.

The propeller shaft cradle 170 may further comprise cradle brace members173A and 173B. Each brace member 173A, B may bridge the offset betweenmotor channel 162 and the propeller shaft channel 174. Each cradle bracemember 173A, B may comprise a plate extending from edges of the cut-out165 in the motor channel 162 to the side surfaces of the propeller shaftchannel 174. Brace members 173A, B may provide support and stability tothe propeller shaft channel 174 to prevent relative displacement betweenthe first motor 101 and first propeller 104, including the gearing thatties the two components.

The first motor cradle 160 and the propeller shaft cradle 170 may befurther supported from flexing, which may cause instability in poweredflight, by bracing members 167A and 167B supporting an inboard side ofthe first motor cradle 160. The bracing members 167A, B may comprise acurved structure extending from a surface of the first arm 102 to a sidesurface of the first motor cradle 160. The curved surface may functionsubstantially to prevent pitching during flight or in response to a hardlanding of the first motor cradle 160 and the propeller shaft cradle 170back towards the center pod assembly 500.

Referring to FIGS. 2, 4, 5A, 9, and 10, in an embodiment, the rotorassemblies 100, 200, 300, and 400 may further comprise a torque transferassembly 180. In reference to the first rotor assembly 100 components,the torque transfer assembly 180 may operably couple the motor shaft 109to the first propeller 104. In some embodiments, the torque transferassembly 180 may comprise the motor gear 115 fixed to the motor shaft109.

In some embodiments, torque is transferred to the motor gear 115 fromthe motor shaft 109 by a non-circular “D” shaped portion of the motorshaft. A central aperture in the motor gear 115 for receiving the motorshaft 109 may comprise a matching D-shape. The D-shape in the motorshaft may be machined flat at an initially circular section in the motorshaft 109. In other embodiments, the motor gear 115 may be attached tothe motor shaft 109 by chemical bonding or by mechanical fasteners, suchas a pin. In other embodiments, the motor gear 115 is formed integrallywith the motor shaft 109.

In an embodiment, the torque transfer assembly 180 may further comprisea first gear 182 mounted co-axially with the propeller shaft 107 in thepropeller shaft cradle 170. The first gear 182 may be configured tomechanically mesh with the motor gear 115 to transfer torque from themotor shaft 109 to the propeller shaft 107 and to support powered flightof the rotorcraft 1000. In a particular embodiment, the gear reductionratio between the motor gear 115 and first gear 182 may be about 78/11or 7.1:1.

The propeller shaft 107 and first propeller 104 may be mounted in thepropeller shaft cradle and supported for rotation by a first bearing117A and a second bearing 117B. The first bearing 117A may be a ballbearing with a central aperture. The first bearing 117A may bepositioned against a first internal ridge 166A that extends along theinternal walls of propeller shaft channel 174 proximal to the bottom endof the propeller shaft channel 174.

The propeller shaft 107 may comprise a shaft ridge 119 at a base end ofthe propeller shaft 107. The propeller shaft 107 may be inserted axiallyinto the bottom end of the propeller shaft channel 174 and through thecentral aperture of the first bearing 117A to constrain the firstbearing 117A between the shaft ridge 119 and the first internal ridge166A.

The second bearing 117B may comprise a ball bearing with a centralaperture and may be positioned against a second internal ridge 166B thatextends along internal walls of the propeller shaft channel 174 proximalto the top end of the propeller shaft channel 174. The propeller shaft107 may extend through the central aperture of the second bearing 117Band through the top end 163 of the propeller shaft channel 174.

A portion of the propeller shaft 107 may extend out of and abovepropeller shaft channel 174. The propeller shaft 107 may comprise anon-circular profile 169 extending along a length of the propeller shaft107. The non-circular profile 169 may be configured to extend through acentral aperture in the first gear 182 and mate with a non-circularprofile of the central aperture for the transfer of torque from thefirst gear 182 to the propeller shaft 107.

The first gear 182 may be mounted on the shaft 107 between the secondbearing 117B and the first propeller 104. The first gear 182 may bepositioned substantially within the perimeter of the gear rim 176. Aportion of the gear rim 176 may extend above the plane in which thefirst gear 182 rotates, providing protection to the first gear 182 fromforeign objects impacting the first gear 182 from above. The spokes175A-E, which may extend in a plane beneath the plane in which the firstgear 182 rotates, providing protection to the first gear 182 fromimpacts to the first gear 182 from foreign objects approaching frombeneath the first gear 182. The first propeller 104, which may alsoextend and rotate in a plane above the plane in which the first gear 182rotates, may also provide protection to the first gear 182 from foreignobjects approaching from above the first gear 182.

The non-circular profile 169 of the propeller shaft 107 may be furtherconfigured to extend through a central aperture a hub channel 133 of ahub 125 of the first propeller 104. The non-circular profile 169 maymate with a non-circular profile of the hub channel 133 to support thetransfer of torque from the propeller shaft 107 to the first propeller104.

In some embodiments, the propeller shaft 107 may be coupled to the firstpropeller 104 by a fastener 123, which may be a screw having a headportion. The fastener 123 may extend through a hub aperture 131 in thehub 125 of the first propeller 104 and threadably couple to a shaftaperture 168, which may extend axially through the portion of thepropeller shaft 107 located within the hub channel 133. The head portionof the screw may be advanced until it sets against a hub ridge withinthe hub 125 to secure the first propeller 104 to the propeller shaft107.

Referring to FIG. 4, the center pod assembly 500 may comprise a firstcover 502 and base 504 coupled to form a housing for partially, orsubstantially, enclosing the control components of the rotorcraft 1000.The base 504 may be configured to be removable from the first cover 502.As shown in FIGS. 11B and 12, in an embodiment, the base 504 may besecured with fasteners 530A-D, for example, screws, extending throughbase apertures 532A-D and threadably coupling into correspondingapertures (not shown) in the underside of the first cover 502.

In some embodiments, the first cover 502 and arms 102, 202, 302, and 402may be integrally formed from a single piece of material. In suchembodiments, the material forming the single piece comprising the firstcover 502 and arms 102, 202, 302, 402 may be composed of a nylon, orsimilar, material. Alternatively, the first cover 502 and arms 102, 202,302, and 402 may, instead, be separate components and may be coupled toone another.

In an embodiment, the base 504 may be composed of nylon, or similar,material. It will be understood by persons of ordinary skill in the artthat the components of the center pod assembly 500 may be made fromother suitable materials (e.g. plastics, metals, wood, and composites)based on the requirements for flight of the rotorcraft 1000 and otherstructural, aesthetic, and cost factors.

Referring to FIGS. 4 and 11A-C, in an embodiment, the base 504 maycomprise a mounting surface 505, side walls 508A-D, a plurality of lightreceptacles 510, a plurality of light openings 512, a plurality of frontwalls 513, and a plurality of locator recesses 518. In an alternativeembodiment, the base 504 may comprise additional, fewer, or differentcomponents.

The base 504 may be implemented with side walls 508A-D for at leastpartially enclosing the controls components, which, in an embodiment,may include a printed circuit board assembly (PCBA) 506, a battery (notshown), and a plurality of light sources 511A-E,

In an embodiment, the side walls 508A-D may each be oriented to form asubstantially vertical surface, as best shown in FIG. 11A. The sidewalls 508A-D may extend upward from a substantially horizontallyoriented surface, a mounting surface 505. The mounting surface 505 mayextend a distance inward from the lower edge of the side walls 508 alongthe perimeter of the base 504 for receiving and coupling components tothe base 504.

As shown in the embodiment of FIG. 11A, the light receptacles 510A-D mayextend from the corners where the side surfaces 508A-D meet. Each lightreceptacle 510A-D may comprise a generally trapezoidal shaped area thatmay partially enclose a light source 511A-D, respectively. In anembodiment, the front walls 513A-D may form the outermost surfacedefining the trapezoidal shape, as best shown in FIG. 11A. The frontwalls 513A-D may each be implemented with a cutout portion, forminglight openings 512A-E.

The light openings 512A-E may be configured to have boundary shape thatis substantially coincident with the cross sectional shape of the collar135 of the support members 106, 206, 306, and 406. As described above,the support members 106, 206, 306, and 406 may couple to the base 504,with the collar 135 sliding into the light openings 512 A-D, trappingthe hoop members 121 within the light receptacles 510 A-D when the base504 is coupled to the first cover 502.

The light openings 512 A-E may also provide a passage through whichlight emitted by the light sources 511 A-E may reach the exterior of thecoupled center pod assembly 500, accessing the inboard ends of thesupport members 106, 206, 306, and 406.

Referring to FIG. 12, the light sources 511A-E may be disposed withinthe center pod assembly 500 and within the substantially horizontalplane of the PCBA 506. The light sources 511A-E may be oriented to faceaway from PCBA 506 and toward light receptacles 510A-E, so the lightsources 511A-E may emit light in a direction substantially towards andthrough light openings 512A-E.

In an embodiment, the light sources 511A-E may be configured to emitlight of any frequency within the visible spectrum. Further, in anembodiment, each light source 511A-E may be configured to emit light ofthe same color, for example, each light source may be configured to emitsubstantially ‘white’ light, or, alternatively some or all of lightsources 511A-E may be configured to emit different ‘colors’ of light.

In an embodiment, the light sources 511A-E may be light emitting diodes(LED). In alternative embodiments, the light source may be anincandescent lamp, electroluminescent lamp, gas discharge lamp, laser,or the like.

In an embodiment, and as shown in FIGS. 12 and 13B, each of the lightsources 511A-E may be implemented with a locator 519A-E. The locators519A-E may be made from a flexible or compliant material such as rubber,plastic, foam, or the like that may be resilient and capable of elasticdeformation. The locators 519A-E may be sized to stretch and fit arounda light source 511A-E, coupling snugly to the light source 511 andmaintaining frictional contact along substantially the entire portion ofthe light source 511 to which the locator 519 is attached.

In a particular embodiment, for example, LEDs may be provided as a lightsource and rubber, or plastic, O-rings may be provided as a locator. Insuch an embodiment, the O-ring may be configured to have an internalcircumference length of slightly less than the perimeter length of theLED to which the O-ring is applied. The O-ring may be stretched to fitover the LED and grip the LED along the O-ring inner surface, providingfrictional resistance to removal of the placed O-ring. With the O-ringin place, the LED may be positioned, oriented, and secured in placethrough fixing the location of the affixed O-ring.

Referring to FIGS. 11, 12, and 13A-C, in an embodiment, the base 504 mayfurther comprise a plurality of locator recesses 518A-D for receiving,positioning, and securing locators 519A-D, thereby setting the locationand orientation of the light source 511A-D to which the locator 519A-Dis affixed. The locator recesses 518A-D may each be a downwardlyextending depression formed into the mounting surface 505 and disposedat the lower portion of each light receptacle 510A-D. The locatorrecesses 518A-D may be configured to direct the light emitted from thereceived light source 511A-D in a desired direction, such as towards alight opening 512A-D so that the light may access the inboard ends ofthe support members 106, 206, 306, and 406.

In an embodiment, a fifth locator recess 518E may be provided forsetting the location and orientation of the taillight, light source511E. The locator recess 518E may be located adjacent to side surface508A and may also be configured to support, position, and secure a lightsource 511E, so that the light source 511E may partially pass throughthe light opening 512E.

Referring to FIG. 12, the first cover 502 may comprise locator cradles520A-D extending from an undersurface of the first cover 502 at the baseof each arm 102, 202, 302, and 402. Each locator cradle 520A-D maycomprise a first column 522A-D spaced from a second column 523A-D. Thewidth between the first column 522A and the second column 523A may beconfigured to snugly fit each respective locator 519A-D mounted aroundeach respective light source 511A-D in an interference fit. A locatorcradle 520E may be configured in a similar manner to locator cradles520A-D for supporting the light source 511E. The locator cradle 520E maycomprise a first column 522E and second column 523E spaced from eachother for snugly fitting the light source 511E, having the locator 519Ebetween the columns 522E, 523E.

As shown in FIGS. 11B, 12, 13B, and 13C, in an embodiment the locatorcradles 520A-E may be disposed and oriented within the first cover 502at locations corresponding to, and aligning with the locations of thelocator recesses 518A-E of the base 504, so that the locator cradles520A-E and the locator recesses 518A-E may simultaneously receive thelocators 519A-E when the base 504 and first cover 502 are coupled. Inalternative embodiments, the locator recesses 518, alone, or,alternatively, the locator cradles 520, alone, may be provided forreceiving and setting the position of the locators 519 and light sources511 provided.

Referring to FIG. 4, the PCBA 506 may comprise a main circuit boardincluding components 507 that would be known to persons of ordinaryskill in the art, including but not limited to a control processor, atransceiver, a radio-frequency antenna, sensors (e.g. gyroscopic sensorsand accelerometer sensors) motor controllers, and a data interface. ThePCBA 506 may also comprise power connectors for each light source511A-E.

Referring to FIGS. 12 and 13C, the light sources 511A-E may couple tothe PCBA 506 at locations along the perimeter of the PCBA 506. Referringto FIGS. 4, 12, and 13A-C, in a particular embodiment, the light sources511A-E may be implemented with locators 519A-E and sets of leads 526A-Efor electrically coupling the light sources 511A-E to the PCBA 506. Eachset of leads 526A-E may comprise substantially rigid metal conductors,and may be soldered to the circuit board of the PCBA to create asubstantially rigid connection between each light source 511A-E and thecircuit board.

According to the embodiment shown in FIGS. 12 and 13C, the PCBA 506 maybe coupled to the underside of the first cover 502 by setting each lightsource 511A-E having a locator 519A-E mounted around each light source511A-E into each respective locator cradle 520A-E so that each locator519A-E is snugly fit in an interference fit with each locator cradle520A-E. In this configuration, the circuit board of the PCBA 506 may becoupled to the first cover 502 without making contact with any internalsurfaces of the first cover 502.

The base 504 may be coupled to the first cover 502 as described above,and locator recesses 518A-E may receive the lower portion of thelocators 519A-E and fix the location of each light source 511A-E withinthe center pod assembly 500. The PCBA 506 may be operably coupled toboth the first cover 502 and base 504 within the formed center podassembly 500 without the PCBA 506 contacting any portion of the interiorsurface of the center pod assembly 500.

In this arrangement, the PCBA 506 may also be vibrationally isolatedfrom the center pod assembly 500 and rotor assembly 100, 200, 300, and400 components. The resilient and elastically deformable material of thelocators 519A-E may provide vibration absorbing protection to the PCBA506, insulating the PCBA 506 from impacts during rotorcraft 1000operation as well as from vibrations induced into the rotorcraft 1000through rotation of the propellers 104, 204, 304, and 404.

Vibrationally isolating the controls components of the rotorcraft 1000may provide the advantages of prolonging the useful life of therotorcraft 1000 through increased crash damage resistance and may alsoimprove rotorcraft control and stability during flight, with thecontrols components protected from vibrations that may affect datacollected by controls components for use in flight control.

Referring to FIG. 2, the first cover 502 may further comprise covermembers 528A-D comprising bars crossing between opposing first and thirdarms 102, 302 and second and fourth arms 202, 402. The cover members528A-D may be configured to crossover the PCBA 506 and provideprotection to the PCBA 506 from impacts and foreign objects. It will beunderstood by persons of ordinary skill in the art that the covermembers 528A-D may form other patterns or form a continuous surfaceaccording to design requirements for the rotorcraft 1000.

Referring to FIGS. 3 and 4, the first cover 502 may further comprise aconnector clip 536 configured to hold a power connector (not shown)extending from the circuit board of the PCBA 506. The connector clip 536may comprise a shelf 538 extending generally perpendicular to the sidesurface 508C. A rail 539 may extend from an end of the shelf 538generally parallel to the side surface 508C.

A tab 540 may extend from an end of the rail 539. The side surface 508C,shelf 538, and rail 539 may form at least a partially enclosed space forretaining a power connector configured to plug into a connector from abattery (not shown). The tab 540 may be configured to clip onto a sidesurface of a power connector to lock the power connector into place. Theshelf 538 and rail 539 may be bent away from the side surface 508C torelease the tab 540 from the power connector.

Referring to FIG. 11, the base 504 may further comprise a batteryreceptacle 514 configured to hold a substantially prismatically-shapedbattery (not shown) to support operation of the rotorcraft 1000. Thebattery receptacle 514 may comprise support plates 515A, B extendingwithin a first plane and cross bars 516A, B extending within a secondplane offset from the first plane.

The cross bars 516A, B may be offset from each other by distanceconfigured to support a length of a battery. A support beam 517 mayextend between the cross bars 516A, B to further support an underside ofa battery. The cross bars 516A, B may further comprise an approximatelyninety (90) degree bend configured to accommodate a depth of a batteryand support sides of the battery.

The battery may be inserted in the battery receptacle 514 through abattery opening 521 in the base 504 and slid into the space formed byand between the support plates 515A, B and the cross bars 516A, B. Thetabs 524A, B may extend in a direction substantially perpendicular tothe direction of insertion of the battery and may function as stops toprevent the battery from falling out through an opening in the batteryreceptacle 514 opposite from the battery opening 521. Additionally, thetabs 524A, B may allow the battery to be aligned properly with thecenter of gravity C1.

Referring to FIGS. 1 and 4, the center pod assembly 500 may furthercomprise a pod cover 542 configured to couple on a top surface of thefirst cover 502. The pod cover 542 may comprise aesthetically pleasingcurvatures, designs, and other features. In some embodiments, the podcover 542 may be made of a plastic, and may further comprise a two-toneplastic, for example black and red.

Referring to FIGS. 2, 4, and 12, the pod cover 542 may couple to thefirst cover 502 by fasteners 535A-C (e.g. screws) extending throughsecond cover apertures 534E-G in the pod cover 542 and threadablycoupling with corresponding apertures (not shown) in the underside ofthe pod cover 542.

Having thus described the present invention by reference to certain ofits exemplary embodiments, it is noted that the embodiments disclosedare illustrative rather than limiting in nature and that a wide range ofvariations, modifications, changes, and substitutions are contemplatedin the foregoing disclosure and, in some instances, some features of thepresent invention may be employed without a corresponding use of theother features. Additional details are presented the Appendix attachedhereto and incorporated by reference for all purposes. Many suchvariations and modifications may be considered desirable by thoseskilled in the art based upon a review of the foregoing description ofexemplary embodiments. Accordingly, it is appropriate that any claimssupported by this description be construed broadly and in a mannerconsistent with the scope of the invention.

The invention claimed is:
 1. A radio controlled model rotorcraft havingan electronics compartment, the model rotorcraft comprising: a circuitboard; at least one light source electrically coupled to the circuitboard; and a housing, the housing comprising: a first frame; a secondframe removably coupled to the first frame; and one or more housinginner surfaces; wherein the circuit board is mounted to the first frameand the second frame by the at least one light source; wherein thecircuit board is disposed within the housing spaced apart from eachhousing inner surface; and at least one rotor assembly, the at least onerotor assembly comprising at least one arm extending from the housingand at least one rotorcraft component.
 2. The model rotorcraft of claim1, further comprising: the first frame comprising at least one firstrecess, the at least one first recess receiving the at least one lightsource; and wherein the circuit board is mounted to the first frame andthe second frame by the at least one light source received within the atleast first recess.
 3. The model rotorcraft of claim 2, furthercomprising at least one locator member coupled to the at least one lightsource.
 4. The model rotorcraft of claim 3, wherein the at least onelocator member coupled to the at least one light source comprises anelastically deformable material.
 5. The model rotorcraft of claim 4,wherein the at least one locator member coupled to the at least onelight source is configured to at least partially absorb vibration causedby operation of the at least one rotorcraft component of the at leastone rotor assembly.
 6. The model rotorcraft of claim 4, wherein the atleast one locator member coupled to the at least one light sourcecomprises a continuous loop of material.
 7. The model rotorcraft ofclaim 2, the second frame further comprising at least one second recess,the at least one second recess cooperating with the at least one firstrecess to receive and secure the at least one light source.
 8. The modelrotorcraft of claim 7, wherein the position of the at least one lightsource received within the at least one first recess and the at leastone second recess is fixed by the respective first and second recessesagainst movement in at least three orthogonal directions.
 9. The modelrotorcraft of claim 2, wherein the at least one light source received bythe at least one first recess is secured against movement in at leastone direction.
 10. The model rotorcraft of claim 1, the housing furthercomprising at least one opening passing outwardly through at least oneof the one or more inner surfaces of the housing, wherein the at leastone opening is optically paired with, and receives light most intenselyfrom, the at least one light source.
 11. The model rotorcraft of claim1, wherein the circuit board is mounted within the housing solely by aplurality of the light sources.
 12. A radio controlled model rotorcraft,comprising: a circuit board; at least one first light sourceelectrically coupled to the circuit board; and a housing, comprising: afirst frame, at least a portion of the first frame comprising at leastone first light securing surface; a second frame coupled to the firstframe; and wherein the at least one first light securing surface securesat least a portion of the at least one first light source between thecoupled first and second frames; wherein the circuit board is mounted tothe first frame by the at least one first light source secured by the atleast one first light securing surface; and at least one rotor assemblycomprising an arm, the arm further comprising at least one lighttransmitting channel extending from the housing, the at least one lighttransmitting channel configured to allow light from the at least onefirst light source to be emitted beyond the housing and into the atleast one light transmitting channel.
 13. The model rotorcraft of claim12, wherein at least a portion of the at least one first light source isdisposed within at least a portion of the at least one lighttransmitting channel.
 14. The model rotorcraft of claim 12, wherein thelight transmitting channel comprises light conducting material, andwherein the light transmitting channel forms at least a portion of asocket, the socket receiving at least a portion of the at least onefirst light source and transmitting at least a portion of light emittedfrom the at least one first light source into the light transmittingchannel.
 15. The model rotorcraft of claim 12, wherein at least aportion of the second frame comprises at least one second light securingsurface; and wherein the at least one second light securing surfacesecures at least a portion of the at least one first light sourcebetween the coupled first and second frames.
 16. The model rotorcraft ofclaim 15, wherein the position of the first light source is fixed in atleast three orthogonal directions.
 17. The model rotorcraft of claim 12,further comprising at least one locator member coupled to the at leastone first light source, the at least one first light source at leastpartially received by the first frame.
 18. The model rotorcraft of claim17, wherein the at least one locator member comprises an elasticallydeformable material.
 19. The model rotorcraft of claim 17, wherein theat least one locator member is configured to at least partially isolatethe circuit board from vibration caused by operation of rotorcraftcomponents spaced apart from the circuit board.
 20. The model rotorcraftof claim 17, wherein the at least one locator member comprises acontinuous loop of material and is disposed around the at least onefirst light source.
 21. A compartment for receiving an electroniccomponent of a radio controlled model rotorcraft, comprising: a firstframe a circuit board; at least one light source electrically coupled tothe circuit board; wherein the first frame receives and at leastpartially encloses the at least one light source; wherein the circuitboard is mounted within the first frame by the at least one lightsource; wherein the circuit board is disposed within the first framespaced apart from the inner surfaces of the first frame; and wherein thefirst frame comprises at least one opening passing outwardly through asurface of the first frame, the at least one opening optically pairedwith, and receiving light from the at least one light source.
 22. Thecompartment of claim 21, wherein the first frame comprises at least onefirst recess, the at least one first recess receiving the at least onelight source.
 23. The compartment of claim 22, wherein the at least onelight source received by the first recess is secured against movement inat least one direction.
 24. The compartment of claim 23, furthercomprising at least one locator member coupled to the at least one lightsource received within the at least one first recess.
 25. Thecompartment of claim 24, wherein the at least one locator membercomprises a loop of an elastically deformable material, configured tosnugly fit around the at least one light source.
 26. The compartment ofclaim 25, wherein the inner surface of the at least one locator membergrips the at least one light source, providing frictional resistance toremoval of the locator member from the light source.
 27. A compartmentfor receiving an electronic component of a radio controlled modelrotorcraft, comprising: a housing at least partially forming anenclosure; a circuit board at least partially enclosed within thehousing, the circuit board comprising a substrate portion disposedsubstantially within a first plane; and at least one light sourcesecured to and electrically coupled to the circuit board; wherein the atleast one light source is oriented to extend substantially away from thecircuit board, along a direction substantially aligned with the firstplane; and wherein the circuit board is disposed within the housing andspaced apart from each inner surface of the housing.
 28. The compartmentof claim 27, wherein the at least one light source comprises one or moreleads, each lead soldered to the circuit board proximal to an outer edgeof the substrate portion.
 29. The compartment of claim 27, wherein thehousing comprises at least one opening passing through at least aportion of a surface of the housing, the at least one opening disposedin a plane substantially orthogonal to the first plane.
 30. Thecompartment of claim 27, wherein the housing comprises at least oneopening passing through at least a portion of a surface of the housing,wherein the at least one opening optically paired with, and receiveslight most intensely from, the at least one light source.